Environmental Impact of Aviation and Sustainable Solutions

Environmental Impact of Aviation and Sustainable Solutions is a compilation of review and research articles in the broad field of aviation and the environment. Over three sections and thirteen chapters, this book covers topics such as aircraft design and materials, combustor modeling, atomization, airport pollution, sonic boom and street noise pollution, emission mitigation strategies, and environmentally friendly contributions from a Russian aviation pioneer. This volume is a useful reference for both researchers and students interested in learning about various aspects of aviation and the environmen

An Assessment of Technology for Turbojet Engine Rotor Failures

Design considerations, objectives, and approaches used in containing rotor burst debris are discussed. Methods are given for determining the fracture resistance of various materials used in providing lightweight shielding from fragment impact

Radar Technology

In this book “Radar Technology”, the chapters are divided into four main topic areas: Topic area 1: “Radar Systems” consists of chapters which treat whole radar systems, environment and target functional chain. Topic area 2: “Radar Applications” shows various applications of radar systems, including meteorological radars, ground penetrating radars and glaciology. Topic area 3: “Radar Functional Chain and Signal Processing” describes several aspects of the radar signal processing. From parameter extraction, target detection over tracking and classification technologies. Topic area 4: “Radar Subsystems and Components” consists of design technology of radar subsystem components like antenna design or waveform design

Aircraft Safety and Operating Problems

Results of NASA research in the field of aircraft safety and operating problems are discussed. Topics include: (1) terminal area operations, (2) flight dynamics and control; (3) ground operations; (4) atmospheric environment; (5) structures and materials; (6) powerplants; (7) noise; and (8) human factors engineering

Preliminary design of a supersonic Short Takeoff and Vertical Landing (STOVL) fighter aircraft

The preliminary design study of a supersonic Short Takeoff and Vertical Landing (STOVL) fighter is presented. A brief historical survey of powered lift vehicles was presented, followed by a technology assessment of the latest supersonic STOVL engine cycles under consideration by industry and government in the U.S. and UK. A survey of operational fighter/attack aircraft and the modern battlefield scenario were completed to develop, respectively, the performance requirements and mission profiles for the study. Three configurations were initially investigated with the following engine cycles: a hybrid fan vectored thrust cycle, a lift+lift/cruise cycle, and a mixed flow vectored thrust cycle. The lift+lift/cruise aircraft configuration was selected for detailed design work which consisted of: (1) a material selection and structural layout, including engine removal considerations, (2) an aircraft systems layout, (3) a weapons integration model showing the internal weapons bay mechanism, (4) inlet and nozzle integration, (5) an aircraft suckdown prediction, (6) an aircraft stability and control analysis, including a takeoff, hover, and transition control analysis, (7) a performance and mission capability study, and (8) a life cycle cost analysis. A supersonic fighter aircraft with STOVL capability with the lift+lift/cruise engine cycle seems a viable option for the next generation fighter

A cumulative index to the 1973 issues of Aeronautical engineering: A special bibliography

This publication is a cumulative index to the abstracts contained in NASA SP-7037 (28) through NASA SP-7037 (39) of Aeronautical Engineering: A Special Bibliography. NASA SP-7037 and its supplements have been compiled through the cooperative efforts of the American Institute of Aeronautics and Astronautics (AIAA) and the National Aeronautics and Space Administration (NASA). This cumulative index includes subject, personal author, corporate source, contract, and report number indexes

The development of a low-cost research R.P.V. system

Flight testing is recognised to be the definitive validation of an aerodynamic concept or of an aircraft configuration’s performance. However, flight testing of manned aircraft presents concerns for safety and increasingly prohibitive cost requirements. Complementing wind tunnels, an instrumented Remotely Piloted Vehicle (RPV) is a valuable tool for aeronautical research, with which many aspects of flight mechanics and applied aerodynamics can be investigated economically before the final design of the full size prototype. The aim of this research project is to develop a research RPV system with a low cost emphasis. This thesis details the development, design, construction, and testing of an RPV and its integration into a flight system including an instrumentation payload, a real-time telemetry downlink, data acquisition and processing equipment and software. There have been many innovations in both hardware and software in order to create an RPV system which is small, safe, inexpensive, and yet reliable. Limitations of some low-cost components were amply compensated through local modifications and careful calibrations. A modified one quarter scale R/C model of the Bellanca Citabria was utilised as the basic test vehicle. Appropriate transducers and ancillary instrumentation were developed specifically to meet system requirements. The data acquisition system is able to display flight data in real time whilst recording, thus providing valuable feedback to the pilot, and allowing for post-flight data-processing. Comparisons between flight data and video image records demonstrate the accuracy of the data acquisition system. Each component of the RPV system is recognised to have the potential for enhancement to improve accuracy and reliability. However, the achievement of a set of reasonable goals has demonstrated the feasibility of the original concept. The realisation of a workable RPV system is not an end to itself, but leads to the commencement of further research, using the current work as a baseline. Proposed applications for the RPV system include research into applied aerodynamics and flight mechanics

Altimetric system: Earth observing system. Volume 2h: Panel report

A rationale and recommendations for planning, implementing, and operating an altimetric system aboard the Earth observing system (Eos) spacecraft is provided. In keeping with the recommendations of the Eos Science and Mission Requirements Working Group, a complete altimetric system is defined that is capable of perpetuating the data set to be derived from TOPEX/Poseidon, enabling key scientific questions to be addressed. Since the scientific utility and technical maturity of spaceborne radar altimeters is well documented, the discussion is limited to highlighting those Eos-specific considerations that materially impact upon radar altimetric measurements

Proceedings of the 2018 Canadian Society for Mechanical Engineering (CSME) International Congress

Published proceedings of the 2018 Canadian Society for Mechanical Engineering (CSME) International Congress, hosted by York University, 27-30 May 2018